Electronic equipment module mounting apparatus and method

ABSTRACT

An equipment module, a module retention device, as well as a system and a method for mounting equipment modules are disclosed. The modules can be installed without tools, using the retention device. Each module includes a chassis unit which slides into a unit rack, which is in turn attached to a mounting frame. The entire assembly may be mounted to an instrument panel. The module retention device is attached to the chassis unit, typically engaging a slot on the rack. A rotating fastener secures the retention device in the engaged position. The method includes inserting an electronic module into the open end of a unit rack, sliding an engagement lug attached to a cam lever into engagement with a slot on the rack, electrically coupling a connector on the module with a connector on the rack, and attaching the rack to the mounting frame.

RELATED APPLICATION

This application is a continuation of application Ser. No. 10/086,482filed Feb. 28, 2002, now U.S. Pat. No. 6,549,424 which is incorporatedherein by reference.

FIELD OF THE INVENTION

The invention relates generally to mounting devices and methods ofmounting electronic equipment. More particularly, the invention relatesto mounting devices and methods of mounting avionic equipment in anaircraft.

BACKGROUND OF THE INVENTION

Electronic equipment and devices in general can be incorporated intoincreasingly smaller packages. In the aviation industry, instrumentationand other electronic equipment operates in an increasingly integratedand autonomous fashion. Such equipment, termed “avionics”, or theelectronic instrumentation devices used in an aviation setting,including electronic sensors, communications equipment, navigationequipment, and displays, is therefore also subject to trends inminiaturization and integration, as used in aircraft of all sizes.

Pricing of electronic equipment for aircraft is competitive, and not allaircraft require the same combination of instrumentation options. Tolower costs and increase the number of end user options, moreflexibility in avionic equipment is needed. In response to the need forflexibility, avionics have moved toward modular installations. Forexample, a communication system, a transponder, and a navigation systemcan each be manufactured as separate modules, which are individuallyselected for an aircraft based on cost and the needs of the particularapplication. Modular designs are individually replaceable, whichfacilitates aftermarket upgrades, and inexpensive replacement/repairoperations.

Because of the limited space available on any given aircraft, designersand manufacturers tend to locate avionics modules in areas of theaircraft where space is at less of a premium. Areas commonly used foravionics installation include the rear of the aircraft, or the nosecompartment. Because the pilot or other operator is typically locatedremotely from the modules, controls and data displays for the modulesmounted to the aircraft instrument panel must typically be linked to theoperator through various communications media, such as wires, fiberoptics, and the like.

Space constraints are eased by locating electronic modules in remoteareas of the aircraft. However, such locations make installation,repair, and replacement more difficult, and more expensive.Additionally, when avionics modules are located remotely from theaircraft instrument panel, longer communication lines are needed toexchange data and commands with the operator in the cockpit. Longercommunication lines increase the difficulty of installation, as well asthe risk of communication line failure due to vibration, physicalmovement, and other factors.

In some aircraft, the avionics modules are mounted directly to theinstrument panel, with displays and controls located on the front of themodule, similar to the way stereo equipment is installed in anautomobile. Such configurations reduce problems due to longcommunication lines, however, other limitations arise.

When avionics modules are mounted directly to the instrument panel,space considerations become more significant due to the presence ofaircraft controls directly behind the panel, such as yoke controls andventilation ducts, for example. Displays and controls for the modulesmust also be located in a relatively limited space below the top of theinstrument panel, so as not to impair the pilot's vision. Additionally,other items mounted to the instrument panel must be avoided whenmounting displays and controls. Thus, fitting a group of modules,displays, and controls within a given area on the instrument panelrequires a flexibility in mounting configurations that is lacking incurrent designs.

Another difficulty is encountered when electronic equipment containedwithin avionics modules requires repair/replacement. Each avionicsmodule is typically of a different size and shape, and involves adifferent mounting apparatus. The technician is never sure of what hewill find until viewing the aircraft in person, and even then, it isalmost guaranteed that removing modules will be a time-consuming,labor-intensive process. Usually, several fasteners must be removed,cables re-routed, and other modules may also need removal to accessdesired portions of the particular module in need of repair.

Therefore, there is a need in the art for apparatus, modules, methods,and systems which lend themselves to facilitating repair and replacementof electric equipment modules, such as the avionics modules used inaircraft. A mounting approach for these modules which requires nospecial tools would be especially valuable. Such an approach should alsoprovide enhanced mounting system consistency, and flexibility withrespect to locating displays and controls associated with variousmodules.

SUMMARY OF THE INVENTION

The above mentioned problems with the installation, repair, and/orreplacement of avionics, along with the need for mounting flexibilityare addressed by the present invention, and will be understood byreading and studying the following specification. Systems, devices, andmethods are provided for various avionic equipment mountingconfigurations and apparatus. The systems, devices, and methods of thepresent invention offer more convenient and more flexible mountingconfigurations to support increasingly efficient and integratedinstallation, repair, and replacement of avionics equipment, includedassociated displays and controls.

In one embodiment, an electronic equipment module is provided which canbe installed and removed without using tools. The module includes achassis unit which slides into a unit rack, which in turn is attached toa mounting frame. The entire assembly is typically mounted to a surface,such as the instrument panel of an aircraft. The module is placed intoelectrical communication with the unit rack via mating connectorsattached to the module and to the unit rack using a pivoting cam leverand engagement lug. The lever/lug combination, which is attached to thechassis unit, is capable of slidable engagement with a slot located onthe interior surface of the unit rack, and when fully engaged with theslot, ensures the existence of a mating electrical connection betweenthe aforementioned connectors. The lever can be located so thatsubstantially equal force is applied across all of the matingconnections within the corresponding connectors. A rotating fastenerattached to the cam lever and capable of rotatable engagement with thechassis unit secures the cam lever in the engaged position.

Thus, another embodiment of the invention includes a module retentiondevice, such as the cam lever attached to a pivot and a rotatingfastener. The pivot, which is attached to the chassis unit, can befixedly attached to the cam lever, or rotatably engaged with the camlever. An engagement lug, attached to the cam lever, is adapted forslidable engagement with a slot included in a unit rack. The slotengaged by the lug includes two open-ended sub-slots, typically formedso as to intersect at an obtuse angle.

In another embodiment, the invention includes an electronic equipmentmodule mounting system, which comprises a mounting frame, a plurality ofelectronic equipment modules (each including chassis units, cam levers,lugs, and pivots), and a unit rack coupled to each of the electronicmodules and the mounting frame. The modules can include any type ofavionic or electronic equipment, such as engine and/or airframemonitoring circuitry, a computer, etc. The mounting system can alsoinclude a display unit, perhaps mounted to an instrument panel, locateddirectly in front of the electronic equipment modules. The mountingsystem also includes an embodiment where a motherboard is coupledbetween one or more of the electronic equipment modules and the displayunit.

Finally, the invention includes a method of mounting electronicequipment modules in a mounting frame. The method includes inserting anelectronic module into the open end of a unit rack, sliding the lugattached to a chassis unit of the module into slidable engagement with aslot located on the interior surface of the unit rack, electricallycoupling a connector on the module with a corresponding connector on theunit rack, and attaching the unit rack to the mounting frame. The methodalso includes establishing electrical communication between a displayunit and the electronic equipment module, and mounting the display uniton the mounting frame or to an instrument panel. Of course, the camlever can be fully engaged and secured (using a rotatable fastener)without the use of tools.

These and other embodiments, aspects, advantages, and features of thepresent invention will be set forth in part in the description whichfollows, and in part will become apparent to those skilled in the art byreference to the following description of the invention and referenceddrawings or by practice of the invention. The aspects, advantages, andfeatures of the invention are also realized and attained by means of theinstrumentalities, procedures, and combinations particularly pointed outin the appended claims.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1A is a perspective view of a mounting frame according to anembodiment of the invention;

FIG. 1B is a top view of a mounting system according to an embodiment ofthe invention;

FIG. 1C is a perspective view of a mounting system according to anembodiment of the invention;

FIG. 2 is a perspective view of an electronic equipment module partiallyengaged with a unit rack according to an embodiment of the invention;

FIGS. 3A, 3B, and 3C are side plan views of an electronic equipmentmodule fully, partially, and non-engaged with a unit rack, respectively,according to an embodiment of the invention;

FIGS. 4A, 4B, and 4C are perspective detail views of a unit rackengagement slot and cam lever according to various embodiments of thepresent invention;

FIGS. 5A and 5B are front plan views of an electronic equipment moduleaccording to an embodiment of the present invention;

FIG. 6 is a top view of a mounting system according to an alternativeembodiment ofthe invention; and

FIG. 7 is an avionic instrument panel and mounting system according toan embodiment of the invention.

DETAILED DESCRIPTION OF EMBODIMENTS OF THE INVENTION

In the following detailed description of the invention, reference ismade to the accompanying drawings which form a part hereof, and in whichis shown, by way of illustration, specific embodiments in which theinvention can be practiced. In the drawings, like numerals describesubstantially similar components throughout the several views. Theseembodiments are described in sufficient detail to enable those skilledin the art to practice the invention. Other embodiments can be utilizedand structural, logical, and electrical changes can be made withoutdeparting from the scope of the present invention.

References to directions, such as up, down, above, or below, etc. willhave their normal meaning with the ground being downward when referringto embodiments not used in aircraft. When referring to embodimentsmounted to an aircraft, downwards will refer to the direction towardsthe floor of the aircraft (i.e., to which the landing gear is typicallymounted), regardless of the orientation of the aircraft during flight.When referring to embodiments of the invention that are mounted adjacentto a mounting surface, such as an airplane instrument panel, referencesto the “front” of the panel will refer to a side of the panel that isintended for operator accessibility, while references to the “rear” ofthe panel will refer to the side of the panel that is normally towardsthe nose of the aircraft, and not easily accessible to an aircraftoperator.

In one embodiment, the system and method of the invention for mountingelectronic equipment modules is used in an aircraft, and is attached toa mounting surface within the aircraft, such as the instrument panel.Although this setting is used as an example, the mounting system andmethod described can be used in other settings as well without departingfrom the scope of the invention.

FIG. 1A is a perspective view of a mounting frame according to anembodiment of the invention. The mounting frame 100 includes a pair offirst mounting surfaces 102, each with a plurality of mounting holes 103which permit a range of assembly along the direction 104. The mountingframe 100 also includes a pair of second mounting surfaces 106, eachwith a plurality of mounting slots 107, that enable a range of assemblyalong the direction 108. In the illustrated embodiment, pairs ofmounting surfaces 102, 106 are shown on opposing sides of the mountingframe 100. However, it should be understood that other configurations ofmounting surfaces 102, 106 are contemplated, such as using only a singlemounting surface instead of a pair of surfaces, using more than twomounting surfaces (e.g., using three cooperating mounting surfaces), orusing mounting surfaces that are not on opposing sides of the frame 100.Likewise, the mounting holes 103 and slots 107 shown in FIG. 1A aremerely examples of many possible configurations which can be used forattaching items to the frame 100, using the first and second mountingsurfaces 102, 106.

One skilled in the art will recognize that other configurations formounting will also be operative to secure various items to the frame100. The first mounting holes 103 and the second mounting slots 107 canbe exchanged on their respective mounting surfaces 102 and 106.Similarly, both sets of surfaces 102, 106 can use holes 103, or bothsets of surfaces 102, 106 can use slots for attaching items thereto. Inone possible configuration of the invention, therefore, the firstmounting holes 103 and the second mounting slots 107 can be adapted foruse with a fastener such as a screw. However, other fasteners known tothose skilled in the art, both temporary and permanent, such as rivets,adhesives, bolts and nuts, etc. can also be used without departing fromthe scope of the invention.

FIG. 1B is a top view of a mounting system 109 according to anembodiment of the invention. A number of unit racks 120 are shown. Eachunit rack 120 includes a back plate 124 secured to the unit rack 120 byone or more fasteners 126. In one embodiment, the back plate 124 furtherincludes an electrical connector 128, such as a backplane pin connector.Each unit rack 120 can be attached to the second mounting surface 106 ofthe mounting frame 100. Electronic equipment modules 130 are shown asinsertable into the open ends 131 of, or slidably engagable withcorresponding unit racks 120 along the direction of the arrows 133. Suchmodules 130 can include, but are not limited to including, variousdevices, such as a cellular telephone, an aircraft radio, a transponder,a global positioning system (GPS) receiver, a computer, enginemonitoring circuitry, airframe monitoring circuitry, atmosphericmonitoring circuitry, and/or other devices and equipment, such as a dataacquisition system, which process information from sensors, acquire suchinformation, and communicate the information in various forms.

In one embodiment, each unit rack 120 is specifically sized to accept acorresponding electronic equipment module 130. Prior art configurationsdo not provide the mounting flexibility of a guided slot, such as thatprovided by the combination of a unit frame 120 and a backplate 124,along with the ability to tailor the size of the slot to accommodatespecific electronic equipment modules 130. Rather, prior artconfigurations are limited to uniform module sizes.

FIG. 1C is a perspective view of a mounting system 109 according to anembodiment of the invention, wherein the modules 130 are slidablyengaged with, and attached to, the unit racks 120, which are in turnsecured to the second mounting surfaces 106 via slots 107. As discussedabove, other means of attaching the unit racks 120 to the mounting frame100 are also contemplated.

A display unit 140, including a flat panel, color liquid crystal display(LCD) screen 142, or alternate display units capable of conveying datato the operator using visual devices can be attached to the frame 100,or to an instrument panel, as will be discussed below. In oneembodiment, the display unit 140 includes a number of controls 143 suchas knobs, switches, levers, dials, and the like. The display unit 140 isshown mounted separately from the modules 130, generally following apath along the arrow 144. Mounting the display unit 140 separatelyaccomplishes two objectives: providing additional display mountinglocations, and adding flexibility with regard to the informationdisplayed thereon. Given the construction of the frame 100, any of anumber of three dimensional ranges of mounting locations are possible.Having a separately mounted display unit 140 also provides greaterflexibility in the location of controls 144. Finally, providing a singledisplay unit 140 for a number of electronic modules 130 allowsinformation from several modules 130 to be displayed in an organized,integrated manner on the display unit 140.

As shown in FIGS. 1A and 1C, the unit racks 120 can be mounted along arange of mounting locations 108. The slots 107 of the second mountingsurfaces 106 allow the unit racks 120 to be positioned to one side orthe other of the mounting frame 100. This configuration allows furtherflexibility in locating modules 130, as well as the entire system 109,on a surface, such as a crowded cockpit instrument panel. Unit rack 120usage permits a variety of sizes and shapes of electronic modules 130 tobe mounted in various locations, while maintaining ease of replacement,since the unit racks 120 guide removal and replacement of the modules130. As will be discussed below, the unit racks 120 can also beconfigured with mechanical mechanisms 178 for quickly securing andreleasing the modules 130 from the unit racks 120, as well as formaking/breaking electrical connections as the modules 130 are insertedand removed, respectively, from the unit racks 120.

FIG. 2 is a perspective view of an electronic equipment module partiallyengaged with a unit rack according to an embodiment of the invention.The electronic equipment module 230 includes a chassis unit 250 and acam lever 252 attached to the chassis unit 250 with a pivot 253. Anengagement lug 254 is also attached to the cam lever 252. The pivot 253,which is centered on the axis of rotation “V”, is typically mounted tothe exterior surface 256 of the chassis unit 250. The engagement lug 254can be located so as to be substantially coaxial with the axis of camlever 252 rotation “V”, or offset from the axis “V”(and the pivot 253),as shown. The exterior surface 256 of the chassis unit 250 can besmooth, or variegated, as shown.

The chassis unit 250 also has a rear face 258 to support the mounting ofone or more electric connectors 260, if desired. The exterior surface256 of the chassis unit 250 is capable of slidable engagement with theinterior surface 262 of a unit rack 220, which can include one or moreelectric connectors 266 mounted to the interior surface 262.

The engagement lug 254, attached to the cam lever 252, is capable ofslidable engagement with a slot 268 located on the interior surface 262of the unit rack 220. The connectors 260 are capable of electricallycoupling to the corresponding connectors 266 when the cam lever 252 isin an engaged position. When the cam lever 252 is in a non-engagedposition (as shown in FIG. 2), the location or range of locations whichdefine the non-engaged position being determined by the design andorientation of the cam lever 252 with respect to the slot 268, theconnectors 260 are not electrically coupled with the connectors 266.

The module 230 can also include a rotating fastener 270 attached to thecam lever 252. The fastener 270 is capable of rotatable engagement withthe chassis unit 250 (typically via a threaded orifice 272) so as tosecure the cam lever 252 in an engaged position. The fastener 270 can beany number of types, rotational or non-rotational, similar to oridentical to a screw, a spring-loaded snap, a cam-locking mechanism, aquarter-turn locking fastener, or a Dzus fastener, such as the PVS35stud assembly sold by DFS International, Inc.

Once the module 230 is secured within the unit rack 220, the rack 220(similar to or identical to the rack 120) can be mounted to the frame100 (shown in FIG. 1) using screws or other fasteners inserted into theholes or slots 274 included in the mounting flanges 276 of the unit rack220. Alternatively, the unit rack 220 can be first mounted to the frame100, and then the module 230 can be secured within the unit rack 220. Asnoted above, a module 230 can include any type of electronic circuitry277, such as, for example, a cellular telephone, an aircraft radio, atransponder, a global positioning system (GPS) receiver, a computer,engine monitoring circuitry, airframe monitoring circuitry, atmosphericmonitoring circuitry, and/or other devices and equipment, such as a dataacquisition system, which process information from sensors, acquire suchinformation, and communicate the information in various forms.

FIGS. 3A, 3B, and 3C are side plan views of an electronic equipmentmodule 330 fully, partially, and non-engaged with a unit rack 320,respectively, according to an embodiment of the invention. These figuresserve to clarify the operational relationship, and engagement, betweenthe cam lever 352, the engagement lug 354, and the slot 368. As usedherein, when the cam lever 352 is described as being in a “non-engaged”position, this means that the lever 352 is located substantiallyparallel to a line “W” which coincides with the direction of slidableengagement between the module 330 and the unit rack 320. When the camlever 352 is described as being in an “engaged” position, this meansthat the lever 352 is located with its longitudinal axis (shown as “U”in FIG. 2) substantially perpendicular to the line W which coincideswith the direction of slidable engagement between the module 330 and theunit rack 320.

Thus, referring back to FIG. 1, FIG. 2, and to FIGS. 3A-3C, it can beseen that the invention can be embodied in the form of a moduleretention device 378 including a cam lever 352 extending along alongitudinal axis “U”, attached to an engagement lug 354. The cam lever352 is also attached to a pivot 353 extending along a horizontal axis ofrotation “V”, along with a rotating fastener 270 attached to the camlever 352. The rotating fastener is capable of rotation about arotational axis “T”. It should be noted that the longitudinal,horizontal, and rotational axes are substantially non-parallel.

The retention device 378 can include a fastener 370 of any type,rotating or non-rotating, including any of those described with respectto the fastener 270 (shown in FIG. 2), such as a quarter-turn lockingfastener. The fastener 370 is used to secure the cam lever 352 to thechassis unit 350, typically by engaging an orifice 372, constructedappropriately to receive the fastener 370 and secure the lever 352against vibrational release.

The pivot 353 can be fixedly attached to the cam lever 352, such thatthe pivot 353 rotates freely with respect to the module 330 and chassisunit 350, following the movement of the cam lever 352 throughout an arcδ extending from about 20 degrees to about 180 degrees along a radiuscentered on the rotational axis “V” of the pivot 353. Alternatively, thepivot 353 can be rotatably engaged with the cam lever 352, such that thepivot 353 remains fixed in relation to the module 330 and chassis unit350, and does not move so as to follow the cam lever 352 as it rotatesabout the pivot 353 through the arc 8. In either case, the pivot 353 istypically attached to the chassis unit 350 and the engagement lug 354 isadapted for slidable engagement with a slot 368 included in the unitrack 320, which is in turn placed in sliding engagement with the module330, and the cam lever 352 is capable of rotating through an arc 6having a radius “R” which intersects the horizontal rotational axis “V”at the pivot 353. It should be noted, referring now specifically to FIG.3B, that the connectors 360 include a plurality of contacts 379 (e.g.,sockets or pins), and that the corresponding connectors 366 include acorresponding plurality of contacts 380 (e.g., pins or sockets). As thecam lever 352 is rotated about the pivot 353 axis “V”, from thenon-engaged position (shown in FIG. 3A) to the engaged position (shownin FIG. 3C), the result is the application of a substantially equalforce “F” to each of the pluralities of contacts 379, 380. In fact, thecam lever 352 can be located on the surface 356 of the chassis unit 350,so that the substantially equal mating force “F” applied to thepluralities of contacts 379, 380 is concentrated along a line “W”substantially parallel to a mating direction “X” of pluralities ofcontacts 379, 380.

FIGS. 4A, 4B, and 4C offer perspective detail views of a unit rackengagement slot and cam lever according to various embodiments of thepresent invention. As can be seen in FIG. 4B, the slot 468 includes twoopen-ended sub-slots 481, 482 intersecting to form an angle θ, such asthe acute angle a between the sub-slots 481, 482. Of course, the angle θcan be a right angle (i.e., angle θ=90, as shown in FIG. 4A), or theangle θ can be even greater than 90 degrees, as shown by the dashed arcβ in FIG. 4C. As shown in FIG. 4B, the engagement lug 454 (locatedsubstantially coaxially with the pivot 453) moves about the pivot 453axis of rotation “V” from the first sub-slot 481 into the secondsub-slot 482, such that the module 330 will be most tightly retained atthe intersection 483 of the sub-slots 481, 482, which can be a directintersection, a curve or curved intersection (as shown in FIG. 4A), orany number of other shapes.

Thus, it should be noted that the configuration of the slot 468 can bedescribed in a number of ways. For example, when the angle θ isapproximately 90 degrees, the slot can be described as “substantiallyL-shaped.” The slot 468 can also be more generally described to includetwo open-ended sub-slots 481, 482 intersecting to form a curve 483. Theslot 468 can also be described as including a first open-ended sub-slot481 located approximately parallel to a line “Z” extending from thefront end of the unit rack to the rear end of the unit rack, such thatthe slot 468 also includes a second open-ended sub-slot 482 which is notlocated approximately parallel to a line extending from the front end ofthe unit rack to the rear end of the unit rack. Finally, the slot 468can be more simply described as including two open-ended sub-slots 481,482 intersecting to form an angle θ, such as an acute angle α, or anobtuse angle β, as described above.

Referring now to FIG. 4C, it should be noted that while the pivot 453and engagement lug 454 have been shown as substantially coaxial in FIG.4B, such is not necessarily the case. For example, it can be seen thatthe pivot 453, which is typically located or centered on the axis ofrotation “V” for the cam lever 452, may be offset by a selected distance485 from the center of the location of the engagement lug 454 (alsoshown in FIGS. 2 and 3A-3C). Using this method of construction, when theengagement lug 454 begins to travel into the second open-ended sub-slot482 as it rotates about the pivot 453, then there is an “over-center”engagement action between the engagement lug 454 and the slot 468.

FIGS. 5A and 5B are front plan views of an electronic equipment moduleaccording to an embodiment of the present invention. In these views itis made clear that the retention device 578 can include a fastener 570of any type, rotating or non-rotating, including any of those describedwith respect to the fastener 270 (shown in FIG. 2), such as aquarter-turn locking fastener. The fastener 570 is used to secure thecam lever 552 to the chassis unit 550. In FIG. 5A is shown aquarter-turn locking fastener 570 in the unlocked position, whereas inFIG. 5B is shown a quarter-turn locking fastener 570 in the lockedposition. When in the locked position, the cam lever 552 is preventedfrom vibrating from the engaged position into the non-engaged position.The lever 552 can be released, however, by moving the fastener 570 formthe locked to the unlocked position.

Also apparent from FIGS. 5A-5B are the relative positions of the chassisunit 550 and the unit rack 520. And more specifically, the slidableengagement which occurs between the exterior surface 556 of the chassisunit 550, and the interior surface 562 of the rack unit 520. It can alsobe seen that the slot 568 can be formed entirely on the interior surface562 of the rack unit 520 (as shown in FIG. 5A), or formed so as toinclude the interior surface 562 and the exterior surface 586 of therack unit 520 (as shown in FIG. 5B, as well as in FIGS. 4A-4B).

FIG. 6 is a top view of a mounting system 688 according to analternative embodiment of the invention. The mounting frame 600 is shownwith a motherboard 690 attached to a back side. Electronic modules 630are electrically coupled to the board connectors 692 that are in turnattached to the motherboard 690. Communication lines 694 run from aseparate connector 696 on the motherboard 690 to a display unit 640.

The use of a motherboard 690 allows for greater ease of electricallyconnecting communication lines 694 from the modules 630 to the displayunit 640. While a separate mounting frame for the display unit 640 isnot needed in this configuration, the use of a motherboard dedicatesboard connectors 692, 696 to each electronic module 630, trading offagainst the flexibility of mounting locations for the electronic modules330. To offset this tradeoff somewhat, additional communication lines694 can be introduced as a means for connecting each unit rack 620 tothe motherboard 690. In any case, the display unit 640 in oneconfiguration can still be separately mounted with the mounting frame600 along several ranges of mounting locations. Alternatively, thedisplay 640 can be mounted to an instrument panel, as desired.

The communication lines 694 typically include electrical wires, howeveralternate means of communication such as fiber optic lines, orelectromagnetic radiation could also be used. In one embodiment, thecommunication lines 694 attach to a connector 696 such as a pinconnector. Because the display unit 640 is typically located in closeproximity to the electronic modules 630, the communication lines 694 canbe routed directly, increasing reliability. Because the display unit 640can be separately mounted to the frame 600, or an instrument panel, theelectronic modules 630 are also easily accessible for attachment ofseparate communication lines 694 (not shown). The installation procedureof the mounting system is therefore greatly simplified.

Thus, the invention can also be described as an electronic equipmentmodule mounting system 688 which includes a mounting frame 600, aplurality of electronic equipment modules 630 (similar to or identicalto modules 130, 230, and 330 described hereinabove), and a unit rack 620coupled to each of the electronic modules 630, as well as to themounting frame 600 along a module range of mounting locations 608 withrespect to the mounting frame 600. As noted above, the exterior surfaceof each electronic module 630 is capable of slidable engagement with aninterior surface of the corresponding unit rack 620. Cam levers includedin the modules 630 can be used to remove and replace or install themodules 630 with respect to the unit racks 620. A display unit 640 canbe mounted to an instrument panel, if desired, and located directly infront of the electronic equipment modules 630. The display unit 640 canthen be placed in electronic communication with at least one of theelectronic equipment modules 630, by way of connectors 692, 696, andcommunications lines 694. Any type of electronic circuitry can beincluded in the modules 630, including, for example, a GPS receiver.

FIG. 7 illustrates an avionic instrument panel as a possible mountingsurface for use with the mounting system according to an embodiment ofthe present invention. The mounting surface, in the form of aninstrument panel 725, includes a yoke 735, one or more mounting systems788 according to the present invention, and various otherinstrumentation 795. The mounting systems 788 can include a display unit740, if desired, attached to the instrument panel 725. As can be seenfrom the scale of various elements shown in FIG. 7, even small amountsof flexibility in mounting location along the ranges provided by themounting systems 788 allow a significant number of displays 742 andcontrols 744 to fit on crowded areas of an instrument panel 725.

Returning to FIGS. 1A-1C, 3A-3C, and 5A-5B, a method of mounting anelectronic equipment module in a mounting frame attached to a mountingsurface can be described as follows. The procedure includes insertingthe electronic module 130 into an open end 133 of a unit rack 120. Eachof the modules 130 is similar to or identical to the modules 230, 330,530, and 630 described previously. Therefore, the method also includessliding an engagement lug 354 attached to a cam lever 352 into slidableengagement with a slot 368 located on the interior surface 562 of theunit rack 550, and electrically coupling one or more connectors 360 toone or more corresponding connectors 366 by rotating the cam lever 352into an engaged position (see FIG. 3C) from a non-engaged position (seeFIG. 3A). As this occurs, the engagement lug 354 slides from a firstsub-slot 381 (included in the slot 368) into a second sub-slot 382 (alsoincluded in the slot 368) which intersects the first sub-slot 381. If an“over center” slot 368 design is used, the tension on the lever 352 willincrease as the pivot 354 passes the intersection 383 and slides fromthe first sub-slot 381 into the second sub-slot 383. If a slot 368having an acute angle a is used, the tension will then decrease as thepivot comes to rest within the second sub-slot 383. Of course, as notedpreviously, the unit rack 120 can also be attached to the frame 100before the electronic module 130 is inserted into the unit rack 120.

At this point, the connectors 360, 366 will be electrically coupled. Ifthere is an offset distance 385 introduced between the pivot 353 and theengagement lug 354 locations, any force, vibration-induced or otherwise,which attempts to move the cam lever 352 from the engaged position tothe non-engaged position will have to overcome the over-centerresistance encountered as the engagement lug 354 is moved back fromresting within the sub-slot 382 to the sub-slot 381, across theintersection 383. The method concludes with attaching the unit rack 120to the mounting frame 100.

Referring specifically to FIG. 6, it can be seen that the method canalso include establishing electrical communication between a displayunit 640 and an electronic equipment module 630 (via communication lines694 and connectors 692, 696), and mounting the display unit 640 on themounting frame 600 along a range of mounting locations 608 with respectto the electronic equipment module 630. Of course, each unit rack 620can also be positioned adjacent to the mounting frame 600 along ahorizontal range of mounting locations 608. Establishing electricalcommunication between the display unit 640 and the electronic equipmentmodule 630 typically includes coupling a motherboard 690 between thedisplay unit 640 and the electronic equipment module 630.

Referring back to FIGS. 3A-3C, and assuming a cam lever 352 and fastener370 are used to install the modules 330 into the unit racks 320, themethod can include sliding the engagement lug 354 attached to the camlever 352 into slidable engagement with the slot 368 located on the unitrack and electrically coupling the connectors 360, 366 by rotating thecam lever 352 into an engaged position from a non-engaged position. Themethod can also include rotating the fastener 370 attached to the camlever 352 so as to secure the cam lever 352 in the engaged position,with or without the use of tools (e.g., when a quarter-turn lockingfastener is used as the fastener 370).

CONCLUSION

An improved device, module, system, and method for mounting equipmentmodules, such as those used to enclose avionics, have been disclosed.The inventive concept of providing varying locations for key modularcomponents allows a single mounting system to be used in conjunctionwith several varieties of aircraft, within the crowded confines of aninstrument panel. The system enables module horizontal movement, andsimultaneously, the ability to locate the display unit horizontally orvertically. The multi-dimensional mounting flexibility of the mountingsystem shown allows electronic modules to be mounted in close proximityto a display unit, which greatly increases accessibility of the modulesover prior configurations where modules 130 were housed in the nose orrear of an aircraft. Installation, repair, and replacement are allgreatly simplified with this configuration.

In addition, the present invention provides an apparatus, module,mounting system, and method for more efficient removal and installationof electronic equipment modules, especially those used as avionicsequipment modules in aircraft. A tool-less installation mechanism isprovided, in the form of a module retention device, such as a cam lever,assisted by a rotatable fastener. The system of the invention, alongwith the mechanism, allows aircraft technicians easy access toelectronics located on an aircraft instrument panel, and rapidturnaround repair activity such that spare modules can be inserted andremoved into their corresponding unit racks without using tools, ifdesired.

Although specific embodiments have been illustrated and describedherein, it will be appreciated by those of ordinary skill in the artthat any arrangement which is calculated to achieve the same purpose maybe substituted for the specific embodiment shown. This application isintended to cover any adaptations or variations of the presentinvention. It is to be understood that the above description is intendedto be illustrative, and not restrictive. Combinations of the aboveembodiments, and other embodiments will be apparent to those of skill inthe art upon reviewing the above description. The scope of the inventionincludes any other applications in which the above structures andfabrication methods are used. The scope of the invention should bedetermined with reference to the appended claims, along with the fullscope of equivalents to which such claims are entitled.

It is emphasized that the Abstract is provided to comply with 37 C.F.R.§ 1.72(b) requiring an Abstract that will allow the reader to quicklyascertain the nature and gist of the technical disclosure. It issubmitted with the understanding that it will not be used to interpretor limit the scope or meaning of the claims. In the foregoing DetailedDescription of Embodiments of the Invention, various features aregrouped together in a single embodiment for the purpose of streamliningthe disclosure. This method of disclosure is not to be interpreted asreflecting an intention that the claimed embodiments of the inventionrequire more features than are expressly recited in each claim. Rather,as the following claims reflect, inventive subject matter lies in lessthan all features of a single disclosed embodiment. Thus the followingclaims are hereby incorporated into the Detailed Description ofEmbodiments of the Invention, with each claim standing on its own as aseparate preferred embodiment.

1. An electronic equipment module, comprising: a chassis unit having anexterior surface including a pivot, and a rear face including a firstelectric connector mounted thereon, the exterior surface of the chassisunit capable of slidable engagement with a unit rack including a secondelectric connector mounted to an interior surface of the unit rack; anda cam lever extending along a first axis and rotatable about the pivot,wherein the cam lever includes an engagement lug extending along asecond axis and capable of slidable engagement with a slot included inthe unit rack, wherein the first axis is not parallel to the secondaxis, and wherein the first connector is capable of electricallycoupling to the second connector when the cam lever is in an engagedposition.
 2. The module of claim 1, further including a rotatingfastener attached to the cam lever and capable of rotatable engagementwith the chassis unit so as to secure the cam lever in the engagedposition.
 3. The module of claim 2, wherein the rotating fastener is aquarter-turn locking fastener.
 4. The module of claim 1, wherein the camlever is capable of rotating about the pivot from the engaged positionto the non-engaged position through an arc of about 20 to about 180degrees.
 5. The module of claim 1, wherein the pivot is fixedly attachedto the cam lever.
 6. The module of claim 1, wherein the pivot isrotatably attached to the cam lever.
 7. The module of claim 1, whereinthe slot is substantially L-shaped.
 8. The module of claim 1, whereinthe slot includes two intersecting open-ended sub-slots.
 9. The moduleof claim 1, wherein the slot includes a first open-ended sub-slotlocated approximately parallel to a line extending from a front end ofthe unit rack to a rear end of the unit rack, and wherein the slotincludes a second open-ended sub-slot which is not located approximatelyparallel to a line extending from the front end of the unit rack to therear end of the unit rack.
 10. The module of claim 1, wherein the slotincludes two open-ended sub-slots intersecting to form an obtuse angle.11. The module of claim 1, wherein the slot includes two open-endedsub-slots intersecting to form an acute angle.
 12. The module of claim1, wherein the first connector includes a first plurality of contacts,wherein the second connector includes a second plurality of contacts,and wherein rotating the cam lever about the pivot from the non-engagedposition to the engaged position results in the application of asubstantially equal mating force to each one of the first and secondpluralities of contacts.
 13. The module of claim 12, wherein thesubstantially equal mating force applied to each one of the first andsecond pluralities of contacts is concentrated along a linesubstantially parallel to a mating direction of the first and secondpluralities of contacts.
 14. An electronic equipment module mountingsystem, comprising: a mounting frame adapted for mounting to a mountingsurface; a plurality of electronic equipment modules, wherein at leastone of the electronic equipment modules includes a chassis unit havingan exterior surface including a pivot and a rear face including a firstelectric connector mounted thereon; and a unit rack coupled to the atleast one electronic equipment module and coupled to the mounting framealong a module range of mounting locations with respect to the mountingframe, wherein the exterior surface of the chassis unit is capable ofslidable engagement with a the unit rack including a second electricconnector mounted to an interior surface of the unit rack, wherein a camlever extending along a first axis and rotatable about the pivotincludes an engagement lug capable of slidable engagement with a slotlocated on the unit rack, wherein the engagement lug extends along asecond axis not parallel to the first axis, and wherein the firstconnector is capable of electrically coupling to the second connectorwhen the cam lever is in an engaged position.
 15. The mounting system ofclaim 14, wherein the mounting surface includes a cockpit instrumentpanel.
 16. The mounting system of claim 14, further comprising: adisplay unit located directly in front of the plurality of electronicequipment modules and in electronic communication with at least one ofthe plurality of electronic equipment modules, the display unit beingmounted to an instrument panel.
 17. The mounting system of claim 14,wherein at least one of the electronic equipment modules includesmonitoring circuitry.
 18. The mounting system of claim 17, wherein themonitoring circuitry includes engine monitoring circuitry.
 19. Themounting system of claim 17, wherein the monitoring circuitry includesairframe monitoring circuitry.
 20. A method of mounting an electronicequipment module in a mounting frame attached to a mounting surface,comprising: attaching a unit rack to the mounting frame; inserting theelectronic module into an open end of the unit rack, wherein theelectronic module includes a chassis unit having an exterior surfaceincluding a pivot and a rear face including a first electric connectormounted thereon, the exterior surface of the chassis unit capable ofslidable engagement with the unit rack including a second electricconnector mounted to an interior surface of the unit rack, and a camlever extending along a first axis and rotatable about the pivot;sliding an engagement lug extending along a second axis and attached tothe cam lever into slidable engagement with a slot located on theinterior surface of the unit rack, wherein the second axis is notparallel to the first axis; and electrically coupling the firstconnector to the second connector by rotating the cam lever into anengaged position from a non-engaged position, and sliding the engagementlug from a first sub-slot included in the slot into a second sub-slotincluded in the slot, wherein the first sub-slot intersects the secondsub-slot.
 21. The method of claim 20, further comprising: establishingelectrical communication between a display unit and the electronicequipment module; and mounting the display unit to the mounting surface.22. The method of claim 21, wherein the mounting surface includes aninstrument panel.
 23. The method of claim 21, wherein establishingelectrical communication between the display unit and the electronicequipment module includes coupling a motherboard between the displayunit and the electronic equipment module.
 24. The method of claim 20,further comprising: positioning the unit rack adjacent to the mountingframe along a horizontal range of mounting locations.
 25. The method ofclaim 20, wherein sliding the engagement lug into slidable engagementwith a slot located on the interior surface of the unit rack andelectrically coupling the first connector to the second connector byrotating the cam lever into an engaged position from a non-engagedposition is accomplished without using tools.
 26. The method of claim20, further comprising: rotating a fastener attached to the cam leverand capable of rotatable engagement with the chassis unit so as tosecure the cam lever in the engaged position.
 27. The method of claim26, wherein rotating a fastener attached to the cam lever and capable ofrotatable engagement with the chassis unit so as to secure the cam leverin the engaged position is accomplished without using tools.